CN116231880A - Dual-output wireless power supply equipment and method for space flight device - Google Patents
Dual-output wireless power supply equipment and method for space flight device Download PDFInfo
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- CN116231880A CN116231880A CN202310500245.XA CN202310500245A CN116231880A CN 116231880 A CN116231880 A CN 116231880A CN 202310500245 A CN202310500245 A CN 202310500245A CN 116231880 A CN116231880 A CN 116231880A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J50/00—Circuit arrangements or systems for wireless supply or distribution of electric power
- H02J50/10—Circuit arrangements or systems for wireless supply or distribution of electric power using inductive coupling
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J7/0042—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries characterised by the mechanical construction
- H02J7/0045—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries characterised by the mechanical construction concerning the insertion or the connection of the batteries
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M1/00—Details of apparatus for conversion
- H02M1/0003—Details of control, feedback or regulation circuits
- H02M1/0009—Devices or circuits for detecting current in a converter
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M3/00—Conversion of dc power input into dc power output
- H02M3/22—Conversion of dc power input into dc power output with intermediate conversion into ac
- H02M3/24—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters
- H02M3/28—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac
- H02M3/325—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal
- H02M3/335—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only
- H02M3/33569—Conversion of dc power input into dc power output with intermediate conversion into ac by static converters using discharge tubes with control electrode or semiconductor devices with control electrode to produce the intermediate ac using devices of a triode or a transistor type requiring continuous application of a control signal using semiconductor devices only having several active switching elements
- H02M3/33573—Full-bridge at primary side of an isolation transformer
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- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02M—APPARATUS FOR CONVERSION BETWEEN AC AND AC, BETWEEN AC AND DC, OR BETWEEN DC AND DC, AND FOR USE WITH MAINS OR SIMILAR POWER SUPPLY SYSTEMS; CONVERSION OF DC OR AC INPUT POWER INTO SURGE OUTPUT POWER; CONTROL OR REGULATION THEREOF
- H02M7/00—Conversion of ac power input into dc power output; Conversion of dc power input into ac power output
- H02M7/42—Conversion of dc power input into ac power output without possibility of reversal
- H02M7/44—Conversion of dc power input into ac power output without possibility of reversal by static converters
- H02M7/48—Conversion of dc power input into ac power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode
- H02M7/53—Conversion of dc power input into ac power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal
- H02M7/537—Conversion of dc power input into ac power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters
- H02M7/5387—Conversion of dc power input into ac power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters in a bridge configuration
- H02M7/53871—Conversion of dc power input into ac power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal using semiconductor devices only, e.g. single switched pulse inverters in a bridge configuration with automatic control of output voltage or current
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
- H02J2207/00—Indexing scheme relating to details of circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
- H02J2207/20—Charging or discharging characterised by the power electronics converter
Abstract
The invention provides a double-output wireless power supply device and a method for a space flight device, wherein the double-output wireless power supply device for the space flight device comprises primary side equipment and secondary side equipment; the primary side apparatus includes: the primary side voltage regulating circuit comprises a primary side filter circuit, a primary side inverter circuit, a primary side coupler, a primary side voltage regulating circuit, a primary side control circuit, a primary side isolation driving circuit and a primary side current sampling circuit; the secondary side device includes: the secondary side coupler, the secondary side rectifying circuit, the secondary side voltage stabilizing circuit and the secondary side boosting circuit. The device has wireless power supply and wireless charging functions, can be used in the field of mobile wireless power supply and charging of space flight devices, and can meet the requirement of simultaneous power supply of 28V and 33V power supply interface equipment.
Description
Technical Field
The invention belongs to the technical field of wireless power supply, and particularly relates to a dual-output wireless power supply device and method for a space flight device.
Background
The spacecraft is various aircrafts which operate in space according to the law of celestial mechanics and execute specific tasks such as exploration, development and the like, and when the spacecraft flies in orbit, various load devices are required to be powered so as to ensure the normal operation of the load devices.
In the prior art, a spacecraft power supply device can only supply power to load devices with one power supply interface, the power supply mode is single, and the power consumption requirements of various load devices with different power supply interfaces cannot be met.
Disclosure of Invention
Aiming at the defects existing in the prior art, the invention provides double-output wireless power supply equipment and a method for a space flight device, which can effectively solve the problems.
The technical scheme adopted by the invention is as follows:
the invention provides a double-output wireless power supply device for a space flight device, which comprises primary side equipment and secondary side equipment;
the primary side apparatus includes: the primary side voltage regulating circuit comprises a primary side filter circuit, a primary side inverter circuit, a primary side coupler, a primary side voltage regulating circuit, a primary side control circuit, a primary side isolation driving circuit and a primary side current sampling circuit;
the primary side filter circuit, the primary side inverter circuit and the primary side coupler are connected in series according to the current transmission direction; the input end of the primary side control circuit is respectively connected with the output ends of the primary side voltage regulating circuit, the upper layer control equipment and the primary side current sampling circuit; the output end of the primary side control circuit is connected with the control end of the primary side inverter circuit through the primary side isolation driving circuit; the input end of the primary side current sampling circuit is connected with the output end of the primary side coupler;
the secondary side device includes: the secondary side coupler, the secondary side rectifying circuit, the secondary side voltage stabilizing circuit and the secondary side boosting circuit; according to the current transmission direction, the secondary side coupler, the secondary side rectifying circuit, the secondary side voltage stabilizing circuit and the secondary side voltage boosting circuit are connected in series; the output end of the secondary side booster circuit is connected with the charging end of an external battery; the output end of the secondary side voltage stabilizing circuit is connected with the power utilization end of external equipment;
wherein: the primary side coupler and the secondary side coupler are in non-contact inductive connection.
Preferably, the primary side inverter circuit adopts a full-bridge topology and a series capacitance compensation structure.
Preferably, the primary side control circuit adopts an FPGA chip and is provided with an RS422 interface communication and an analog quantity current acquisition interface.
Preferably, the primary side current sampling circuit adopts a delta-sigma modulation sampling chip.
Preferably, coils of the primary side coupler and the secondary side coupler adopt high-frequency low-impedance litz wires for planar frameless winding;
the end surfaces of the primary side coupler and the secondary side coupler are arranged in a disc type.
Preferably, the secondary side rectifying circuit adopts a full-bridge rectifying topological structure; the secondary side voltage stabilizing circuit adopts an isolated DC-DC.
The invention also provides a power supply method of the double-output wireless power supply equipment for the space flying device, which comprises the following steps:
step 1, filtering the 28V +/-1V direct current through a primary side filter circuit to obtain a filtered direct current;
step 2, the filtered direct current passes through a primary side inverter circuit, and the primary side inverter circuit inverts the filtered direct current into high-frequency alternating current;
wherein: the primary side control circuit is used for performing driving control on the primary side inverter circuit according to the current parameters acquired by the primary side current sampling circuit, so that a primary side current peak value is kept at a constant control of a set value, and a distance of 15mm plus or minus 10mm is further kept between the primary side coupler and the secondary side coupler;
the specific method comprises the following steps:
step 2.1, a primary side current sampling circuit collects a primary side zero-crossing current and a primary side current peak value and transmits the primary side zero-crossing current and the primary side current peak value to a primary side control circuit;
step 2.2, frequency modulation control:
the primary side control circuit compares the acquired primary side zero-crossing current with a primary side zero-crossing current set value, carries out frequency modulation control on output frequency, outputs 96 kHz-120 kHz frequency, and keeps a distance of 15mm plus or minus 10mm between the primary side coupler and the secondary side coupler;
step 2.3, current duty cycle control:
the primary side control circuit outputs a current duty ratio value of 0-45% according to the collected primary side current peak value and the frequency value output in the step 2.2;
step 2.4, driving control of the inverter circuit:
the primary side control circuit controls the driving of the inverter circuit according to the frequency value output in the step 2.2 and the current duty ratio value output in the step 2.3, so that the primary side current peak value is kept at the constant control of the set value;
step 3, high-frequency alternating current flows into the primary side coupler, and an alternating magnetic field is generated under the excitation action of the primary side coupler;
step 4, the secondary side coupler is in non-contact induction connection with the primary side coupler, and the secondary side coupler induces alternating electromotive force through the action of an alternating magnetic field generated by the primary side coupler;
step 5, outputting current with the voltage of 27.5V-28.5V after alternating electromotive force sequentially passes through rectification action of a secondary side rectifying circuit and voltage stabilization action of a secondary side voltage stabilizing circuit;
step 6, a current with the voltage of 27.5V to 28.5V is provided with two branches, one branch is directly connected with external equipment, and electric energy with the voltage of 27.5V to 28.5V is supplied to the external equipment; the other branch is boosted by a secondary side booster circuit, the voltage is boosted to 33V-34V, and the current of 33V-34V voltage is obtained; the external battery is charged by a current of 33V to 34V.
The double-output wireless power supply equipment and the method for the space flying device have the following advantages:
the device has wireless power supply and wireless charging functions, can be used in the field of mobile wireless power supply and charging of space flight devices, and can meet the requirement of simultaneous power supply of 28V and 33V power supply interface equipment.
Drawings
Fig. 1 is a schematic structural diagram of a dual-output wireless power supply device for a space flight device according to the present invention;
fig. 2 is a basic structure diagram of an inverter circuit provided by the invention;
fig. 3 is a driving control diagram of an inverter circuit provided by the invention;
fig. 4 is an end view of a coupler structure according to the present invention.
Detailed Description
In order to make the technical problems, technical schemes and beneficial effects solved by the invention more clear, the invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the invention.
The present invention provides a dual output wireless power supply apparatus usable with a space vehicle, referring to fig. 1, including a primary side apparatus and a secondary side apparatus;
the primary side apparatus includes: the primary side voltage regulating circuit comprises a primary side filter circuit, a primary side inverter circuit, a primary side coupler, a primary side voltage regulating circuit, a primary side control circuit, a primary side isolation driving circuit and a primary side current sampling circuit;
the primary side filter circuit, the primary side inverter circuit and the primary side coupler are connected in series according to the current transmission direction; the input end of the primary side control circuit is respectively connected with the output ends of the primary side voltage regulating circuit, the upper layer control equipment and the primary side current sampling circuit; the output end of the primary side control circuit is connected with the control end of the primary side inverter circuit through the primary side isolation driving circuit; the input end of the primary side current sampling circuit is connected with the output end of the primary side coupler;
the secondary side device includes: the secondary side coupler, the secondary side rectifying circuit, the secondary side voltage stabilizing circuit and the secondary side boosting circuit; according to the current transmission direction, the secondary side coupler, the secondary side rectifying circuit, the secondary side voltage stabilizing circuit and the secondary side voltage boosting circuit are connected in series; the output end of the secondary side booster circuit is connected with the charging end of an external battery; the output end of the secondary side voltage stabilizing circuit is connected with the power utilization end of external equipment;
wherein: the primary side coupler and the secondary side coupler are in non-contact inductive connection.
The specific structure and principle of the primary side device and the secondary side device are described in detail below:
(1) Primary side filter circuit: the method is used for carrying out filtering treatment on the input 28V +/-1V direct current, inhibiting conduction interference, and can inhibit high-frequency signals above 500KHz to below 60dB, thereby reducing high-frequency interference on other devices on the same power supply bus.
(2) Primary side inverter circuit: the full-bridge topology and series capacitance compensation type structure is adopted, and more than 50W of output power of 28V mobile power supply and 33V mobile charging can be provided within a distance of 15 mm+/-10 mm. The circuit structure is shown in figure 2;
(3) Primary side voltage regulating circuit: for regulating the 5V voltage to 3.3V, 1.2V, to provide the primary side control circuit with an operating voltage.
(4) Primary side control circuit: the FPGA chip is adopted, and the FPGA chip is provided with an RS422 interface communication and an analog current acquisition interface, so that the internal working parameters of the equipment can be transmitted to the upper-layer equipment through the RS422 interface, and the current of the primary side of the equipment is acquired.
(5) Primary side isolation drive circuit: isolation voltages of 12V and 5V can be generated, and driving control voltages are provided for the primary side inverter circuit and the primary side current sampling circuit.
(6) Primary side current sampling circuit: a delta-sigma modulation sampling chip is adopted, a sine 3 digital filter is adopted to obtain 15-bit digital quantity, and the sampling resolution of current is 0.0625A.
(7) Primary side coupler and secondary side coupler
The coils of the primary side coupler and the secondary side coupler adopt high-frequency low-impedance litz wires to perform planar frameless winding;
number of winding strands of litz wire
The calculation formula is as follows:
Wireless power supplyAnd a charging device reference operating frequency
The wire diameter of the enameled wire is smaller than 0.2mm and is selected according to the current effective value of 10A, the wire diameter phi of 0.1mm and the current density of 5A/mm 2 The number of the enameled wires in the winding is calculated to be not less than 255 strands.
The magnetic core of the secondary side coupler is made of nanocrystalline alloy material and is formed by cutting and crimping a sheet structure; and the current phase of the primary side coil is changed by designing the resonance capacitance value of the primary side inverter circuit
The electromagnetic interference force during the operation of the equipment is reduced to below 450uN, and the electromagnetic interference force calculation basis is as follows: />
。
In order to ensure that the electromagnetic field distribution is basically unchanged in a radial motion state, the end faces of the couplers on the primary side and the secondary side are distributed in a disc type, the size envelope is less than or equal to phi 190mm multiplied by 20mm, and the shape is shown in figure 4.
(8) Secondary side rectifying circuit
The secondary side rectifying circuit adopts a full-bridge rectifying topological structure, the withstand voltage of a rectifying diode reaches 650V, the withstand voltage of a TVS (transient voltage suppressor) reaches 350V, the maximum current reaches 20A, and the current derating design of 50% is met.
(9) Secondary side voltage stabilizing circuit
The secondary side voltage stabilizing circuit adopts an isolated DC-DC, and can convert 120V-420V input voltage into 28V/13.40A output.
In the application, the 33V charging circuit and the 28V power supply circuit can simultaneously support the operation of external equipment and realize RS422 communication with the external equipment.
The invention also provides a power supply method based on the double-output wireless power supply equipment for the space flying device, which comprises the following steps:
step 1, filtering the 28V +/-1V direct current through a primary side filter circuit to obtain a filtered direct current;
step 2, the filtered direct current passes through a primary side inverter circuit, and the primary side inverter circuit inverts the filtered direct current into high-frequency alternating current;
wherein: the primary side control circuit is used for performing driving control on the primary side inverter circuit according to the current parameters acquired by the primary side current sampling circuit, so that a primary side current peak value is kept at a constant control of a set value, and a distance of 15mm plus or minus 10mm is further kept between the primary side coupler and the secondary side coupler;
the specific method is shown in fig. 3:
step 2.1, a primary side current sampling circuit collects a primary side zero-crossing current and a primary side current peak value and transmits the primary side zero-crossing current and the primary side current peak value to a primary side control circuit;
step 2.2, frequency modulation control:
the primary side control circuit compares the acquired primary side zero crossing current with a primary side zero crossing current set value, carries out frequency modulation control on output frequency, outputs 96 kHz-120 kHz frequency, keeps a distance of 15mm plus or minus 10mm between the primary side coupler and the secondary side coupler, and ensures that the power transmission efficiency of mobile power supply and mobile charging is at least 55%;
step 2.3, current duty cycle control:
the primary side control circuit outputs a current duty ratio value of 0-45% according to the collected primary side current peak value and the frequency value output in the step 2.2;
step 2.4, driving control of the inverter circuit:
the primary side control circuit controls the driving of the inverter circuit according to the frequency value output in the step 2.2 and the current duty ratio value output in the step 2.3, wherein the inverter circuit adopts phase-shifting full-bridge ZVS control to enable the primary side current peak value to be kept at a constant control of a set value; for example, the primary side current peak value is 10A.
Step 3, high-frequency alternating current flows into the primary side coupler, and an alternating magnetic field is generated under the excitation action of the primary side coupler;
step 4, the secondary side coupler is in non-contact induction connection with the primary side coupler, and the secondary side coupler induces alternating electromotive force through the action of an alternating magnetic field generated by the primary side coupler;
step 5, outputting current with the voltage of 27.5V-28.5V after alternating electromotive force sequentially passes through rectification action of a secondary side rectifying circuit and voltage stabilization action of a secondary side voltage stabilizing circuit;
step 6, a current with the voltage of 27.5V to 28.5V is provided with two branches, one branch is directly connected with external equipment, and electric energy with the voltage of 27.5V to 28.5V is supplied to the external equipment; the other branch is boosted by a secondary side booster circuit, the voltage is boosted to 33V-34V, and the current of 33V-34V voltage is obtained; the external battery is charged by a current of 33V to 34V.
Therefore, the invention provides the dual-output wireless power supply equipment and the method for the space flying device, the wireless power supply and charging equipment comprises the primary end and the secondary end, the non-contact distance between the secondary end and the primary end is 15mm plus or minus 10mm, the output power is not lower than 50W, the electromagnetic interference force during the operation of the equipment is reduced to below 450uN, and meanwhile, 27.5V-28.5V power supply of external equipment and 33V-34V charging of external batteries are realized. Therefore, the device has wireless power supply and wireless charging functions, can be used in the field of mobile wireless power supply and charging of space flight devices, and can meet the requirement of simultaneous power supply of 28V and 33V power supply interface equipment.
The foregoing is merely a preferred embodiment of the present invention and it should be noted that modifications and adaptations to those skilled in the art may be made without departing from the principles of the present invention, which is also intended to be covered by the present invention.
Claims (7)
1. A dual output wireless power supply device for a space flight apparatus, comprising a primary side device and a secondary side device;
the primary side apparatus includes: the primary side voltage regulating circuit comprises a primary side filter circuit, a primary side inverter circuit, a primary side coupler, a primary side voltage regulating circuit, a primary side control circuit, a primary side isolation driving circuit and a primary side current sampling circuit;
the primary side filter circuit, the primary side inverter circuit and the primary side coupler are connected in series according to the current transmission direction; the input end of the primary side control circuit is respectively connected with the output ends of the primary side voltage regulating circuit, the upper layer control equipment and the primary side current sampling circuit; the output end of the primary side control circuit is connected with the control end of the primary side inverter circuit through the primary side isolation driving circuit; the input end of the primary side current sampling circuit is connected with the output end of the primary side coupler;
the secondary side device includes: the secondary side coupler, the secondary side rectifying circuit, the secondary side voltage stabilizing circuit and the secondary side boosting circuit; according to the current transmission direction, the secondary side coupler, the secondary side rectifying circuit, the secondary side voltage stabilizing circuit and the secondary side voltage boosting circuit are connected in series; the output end of the secondary side booster circuit is connected with the charging end of an external battery; the output end of the secondary side voltage stabilizing circuit is connected with the power utilization end of external equipment;
wherein: the primary side coupler and the secondary side coupler are in non-contact inductive connection.
2. The dual output wireless power supply apparatus for a space vehicle of claim 1, wherein the primary side inverter circuit is configured in a full bridge topology and in a series capacitance compensation mode.
3. The dual output wireless power supply apparatus for a space vehicle of claim 1, wherein the primary side control circuit is an FPGA chip with an RS422 interface communication and analog current acquisition interface.
4. The dual output wireless power supply apparatus for a space vehicle of claim 1, wherein the primary side current sampling circuit employs a delta-sigma modulated sampling chip.
5. The dual output wireless power supply apparatus for a space flying device according to claim 1, wherein the coils of the primary side coupler and the secondary side coupler are made of litz wire with high frequency and low impedance, and are wound in a plane without a framework;
the end surfaces of the primary side coupler and the secondary side coupler are arranged in a disc type.
6. The dual output wireless power supply apparatus for a space vehicle of claim 1, wherein the secondary side rectifying circuit employs a full bridge rectifying topology; the secondary side voltage stabilizing circuit adopts an isolated DC-DC.
7. A method of powering a dual output wireless power supply apparatus for a space vehicle as claimed in any one of claims 1 to 6, comprising the steps of:
step 1, filtering the 28V +/-1V direct current through a primary side filter circuit to obtain a filtered direct current;
step 2, the filtered direct current passes through a primary side inverter circuit, and the primary side inverter circuit inverts the filtered direct current into high-frequency alternating current;
wherein: the primary side control circuit is used for performing driving control on the primary side inverter circuit according to the current parameters acquired by the primary side current sampling circuit, so that a primary side current peak value is kept at a constant control of a set value, and a distance of 15mm plus or minus 10mm is further kept between the primary side coupler and the secondary side coupler;
the specific method comprises the following steps:
step 2.1, a primary side current sampling circuit collects a primary side zero-crossing current and a primary side current peak value and transmits the primary side zero-crossing current and the primary side current peak value to a primary side control circuit;
step 2.2, frequency modulation control:
the primary side control circuit compares the acquired primary side zero-crossing current with a primary side zero-crossing current set value, carries out frequency modulation control on output frequency, outputs 96 kHz-120 kHz frequency, and keeps a distance of 15mm plus or minus 10mm between the primary side coupler and the secondary side coupler;
step 2.3, current duty cycle control:
the primary side control circuit outputs a current duty ratio value of 0-45% according to the collected primary side current peak value and the frequency value output in the step 2.2;
step 2.4, driving control of the inverter circuit:
the primary side control circuit controls the driving of the inverter circuit according to the frequency value output in the step 2.2 and the current duty ratio value output in the step 2.3, so that the primary side current peak value is kept at the constant control of the set value;
step 3, high-frequency alternating current flows into the primary side coupler, and an alternating magnetic field is generated under the excitation action of the primary side coupler;
step 4, the secondary side coupler is in non-contact induction connection with the primary side coupler, and the secondary side coupler induces alternating electromotive force through the action of an alternating magnetic field generated by the primary side coupler;
step 5, outputting current with the voltage of 27.5V-28.5V after alternating electromotive force sequentially passes through rectification action of a secondary side rectifying circuit and voltage stabilization action of a secondary side voltage stabilizing circuit;
step 6, a current with the voltage of 27.5V to 28.5V is provided with two branches, one branch is directly connected with external equipment, and electric energy with the voltage of 27.5V to 28.5V is supplied to the external equipment; the other branch is boosted by a secondary side booster circuit, the voltage is boosted to 33V-34V, and the current of 33V-34V voltage is obtained; the external battery is charged by a current of 33V to 34V.
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| CN113162254A (en) * | 2021-04-16 | 2021-07-23 | 中国矿业大学 | Multi-stage pulse switching voltage stabilizing circuit and voltage stabilizing method |
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2023
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2013192332A (en) * | 2012-03-13 | 2013-09-26 | Panasonic Corp | Power conditioner |
| CN106059021A (en) * | 2016-06-23 | 2016-10-26 | 邓星艺 | Wireless charging system employing current control mode |
| CN111628650A (en) * | 2020-06-16 | 2020-09-04 | 西安微电子技术研究所 | DC/DC circuit, SIMO converter, microsatellite power supply system and working method |
| CN113162254A (en) * | 2021-04-16 | 2021-07-23 | 中国矿业大学 | Multi-stage pulse switching voltage stabilizing circuit and voltage stabilizing method |
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